AD/EC 225/6 Amdt 1 Main Rotor Hub Coning Stop Supports (Cth)

AIRWORTHINESS DIRECTIVE

On the effective date specified below, and for the reasons set out in the background section, the CASA delegate whose signature appears below revokes Airworthiness Directive (AD) AD/EC 225/6 and issues the following AD under subregulation 39.001(1) of CASR 1998.  The AD requires that the action set out in the requirement section (being action that the delegate considers necessary to correct the unsafe condition) be taken in relation to the aircraft or aeronautical product mentioned in the applicability section: (a) in the circumstances mentioned in the requirement section; and (b) in accordance with the instructions set out in the requirement section; and (c) at the time mentioned in the compliance section.

Eurocopter EC 225 Series Helicopters

AD/EC 225/6 Amdt 1 Main Rotor Hub Coning Stop Supports 4/2009

Applicability:

Model EC 225 LP helicopters, all serial numbers, except those that have been modified during production with MOD 0743718 or in-service with EUROCOPTER EC225 Service Bulletin (SB) No. 62-007 original issue, or later EASA approved revision.

Requirement:

1.    Carry out a check for cracks in the area of the attachment points on the main rotor hub reinforcement ring of the lugs securing the coning stop support and also of the lugs securing the dome fairing support, in accordance with the instructions given in paragraph 2.B.1 of EUROCOPTER EC 225 Alert Service Bulletin (ASB) No. 05A003 Revision 2 or later EASA approved revision.

2.    If, after the effective date of this Directive, a crack is found in one of the five lugs of the coning stop support or in one of the five lugs of the dome fairing support, remove and replace both the coning stop support assembly and the dome fairing support in accordance with the instructions of SB No. 62-007 original issue, or later EASA approved revision.

3.    Modification of any helicopters in accordance with EUROCOPTER EC 225 SB No. 62-005 (MOD 332A08.0929.00) is no longer allowed.

4.    All components installed and/or modified in accordance EUROCOPTER EC 225 SB No. 62-005 (Modification 332A08.0929.00), are to be removed from service.

Replacement of parts in accordance with the instructions of SB No. 62-007 original issue, or later EASA approved revision, constitutes terminating action for the repetitive checks required by Requirement 1 of this Directive.

To be able to reach a location where the coning stop support assembly or the dome fairing support can be replaced, a ferry flight without the dome fairing itself is permitted on the condition that:

• the dome fairing itself and its attachment screws are removed in accordance with the instructions given in the Note in paragraph 2.B.1.b of ASB
  No. 05A003 Revision 1; and,

• the flight crews are made aware that when flying without the dome fairing, the lateral vibrations of the helicopter significantly increase at speeds between 70 to 120 KIAS.  This may be accomplished by inserting a copy of this Directive into the Normal Procedures section of the Rotorcraft Flight Manual for the duration of the ferry flight.  The lateral vibration phenomenon does not affect flight safety.

Note:  EASA AD 2009-0024 refers.

Compliance:

1.    At intervals of 15 flight hours or 7 days, whichever occurs first; until SB
No. 62-007 is accomplished.

2.    Before further flight.

3.    From the effective date of this directive.

4.    Before further flight, unless already accomplished.

This Amendment becomes effective on 9 April 2009.

Background:

This Directive was issued following reports of cracks and failure of the main rotor hub coning stop support lugs at their attachment points on the reinforcement ring where the dome fairing is secured.  Some further cracks have been reported affecting the dome fairing support assemblies, in particular, but not confined to, those modified to SB No. 62-005.  This Directive requires inspections of the dome fairing support lugs and the removal from service of parts installed during modification in accordance with SB No. 62-005.

Amendment 1 is issued in response to a new EASA AD, which adds the requirement, in case of crack findings, to install the new main rotor hub coning stop support and dome fairing support.  Relevant replacement of parts in accordance with SB No.
62-007 constitutes terminating action for the repetitive checks required by this Directive.

David Villiers
Delegate of the Civil Aviation Safety Authority

25 February 2009